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TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: TSAGI 8% AIRFOIL (tsagi8-il)
Reynolds number: 100,000
Max Cl/Cd: 44.39 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-tsagi8-il-100000-n5.txt
Download as CSV file: xf-tsagi8-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TSAGI 8% AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5524   0.08882   0.08405  -0.0105   1.0000   0.0225
  -8.500  -0.5553   0.08439   0.07968  -0.0133   1.0000   0.0220
  -8.250  -0.5619   0.07966   0.07500  -0.0166   1.0000   0.0217
  -8.000  -0.5689   0.07531   0.07066  -0.0183   1.0000   0.0213
  -7.750  -0.5720   0.07081   0.06614  -0.0200   1.0000   0.0208
  -7.500  -0.5738   0.06612   0.06137  -0.0211   1.0000   0.0203
  -7.250  -0.5740   0.06131   0.05645  -0.0216   1.0000   0.0200
  -7.000  -0.5721   0.05657   0.05154  -0.0215   1.0000   0.0196
  -6.750  -0.5681   0.05192   0.04667  -0.0207   1.0000   0.0192
  -6.500  -0.5626   0.04734   0.04180  -0.0193   1.0000   0.0190
  -6.250  -0.5547   0.04324   0.03737  -0.0176   1.0000   0.0191
  -6.000  -0.5448   0.03966   0.03343  -0.0156   1.0000   0.0201
  -5.750  -0.5334   0.03622   0.02957  -0.0133   1.0000   0.0210
  -5.500  -0.5205   0.03296   0.02584  -0.0108   1.0000   0.0216
  -5.250  -0.5057   0.02982   0.02218  -0.0082   1.0000   0.0220
  -5.000  -0.4884   0.02703   0.01889  -0.0059   1.0000   0.0226
  -4.750  -0.4687   0.02466   0.01601  -0.0039   1.0000   0.0235
  -4.500  -0.4471   0.02294   0.01386  -0.0022   1.0000   0.0254
  -4.250  -0.4274   0.02125   0.01211  -0.0008   1.0000   0.0287
  -4.000  -0.4067   0.01987   0.01058   0.0008   1.0000   0.0315
  -3.750  -0.3868   0.01874   0.00929   0.0026   1.0000   0.0362
  -3.500  -0.3689   0.01780   0.00835   0.0043   1.0000   0.0432
  -3.250  -0.3517   0.01689   0.00740   0.0063   1.0000   0.0531
  -3.000  -0.3345   0.01623   0.00672   0.0083   1.0000   0.0686
  -2.750  -0.3038   0.01541   0.00600   0.0073   0.9927   0.1036
  -2.500  -0.2687   0.01445   0.00538   0.0053   0.9822   0.1844
  -2.250  -0.2382   0.01286   0.00497   0.0039   0.9719   0.4592
  -2.000  -0.1513   0.01221   0.00564  -0.0048   0.9983   0.9435
  -1.750  -0.0860   0.01240   0.00547  -0.0121   1.0000   0.9813
  -1.500  -0.0177   0.01229   0.00508  -0.0207   1.0000   1.0000
  -1.250   0.0197   0.01219   0.00482  -0.0233   0.9813   1.0000
  -1.000   0.0621   0.01212   0.00461  -0.0267   0.9596   1.0000
  -0.750   0.1045   0.01204   0.00440  -0.0301   0.9377   1.0000
  -0.500   0.1445   0.01196   0.00421  -0.0328   0.9143   1.0000
  -0.250   0.1806   0.01190   0.00405  -0.0346   0.8897   1.0000
   0.000   0.2120   0.01187   0.00392  -0.0353   0.8653   1.0000
   0.250   0.2398   0.01187   0.00383  -0.0352   0.8422   1.0000
   0.500   0.2648   0.01190   0.00378  -0.0345   0.8197   1.0000
   0.750   0.2893   0.01194   0.00377  -0.0337   0.7994   1.0000
   1.000   0.3130   0.01200   0.00378  -0.0328   0.7793   1.0000
   1.250   0.3369   0.01207   0.00382  -0.0319   0.7606   1.0000
   1.500   0.3609   0.01216   0.00387  -0.0311   0.7426   1.0000
   1.750   0.3845   0.01226   0.00399  -0.0302   0.7245   1.0000
   2.000   0.4080   0.01237   0.00410  -0.0292   0.7071   1.0000
   2.250   0.4313   0.01249   0.00423  -0.0282   0.6900   1.0000
   2.500   0.4547   0.01263   0.00439  -0.0272   0.6734   1.0000
   2.750   0.4779   0.01278   0.00461  -0.0262   0.6562   1.0000
   3.000   0.5010   0.01294   0.00483  -0.0252   0.6384   1.0000
   3.250   0.5241   0.01311   0.00507  -0.0241   0.6205   1.0000
   3.500   0.5470   0.01329   0.00535  -0.0230   0.6020   1.0000
   3.750   0.5699   0.01348   0.00565  -0.0219   0.5815   1.0000
   4.000   0.5922   0.01369   0.00593  -0.0206   0.5590   1.0000
   4.250   0.6132   0.01388   0.00618  -0.0190   0.5231   1.0000
   4.500   0.6303   0.01420   0.00625  -0.0166   0.4474   1.0000
   4.750   0.6439   0.01508   0.00650  -0.0141   0.3068   1.0000
   5.000   0.6516   0.01729   0.00744  -0.0116   0.0937   1.0000
   5.250   0.6662   0.01888   0.00874  -0.0095   0.0450   1.0000
   5.500   0.6831   0.02002   0.00992  -0.0077   0.0338   1.0000
   5.750   0.6993   0.02122   0.01130  -0.0056   0.0298   1.0000
   6.000   0.7155   0.02235   0.01259  -0.0036   0.0261   1.0000
   6.250   0.7289   0.02392   0.01418  -0.0014   0.0229   1.0000
   6.500   0.7456   0.02544   0.01588   0.0006   0.0217   1.0000
   6.750   0.7643   0.02713   0.01773   0.0024   0.0209   1.0000
   7.000   0.7842   0.02912   0.01994   0.0041   0.0197   1.0000
   7.250   0.8032   0.03106   0.02217   0.0057   0.0181   1.0000
   7.500   0.8205   0.03318   0.02458   0.0073   0.0169   1.0000
   7.750   0.8357   0.03581   0.02758   0.0093   0.0163   1.0000
   8.000   0.8478   0.03869   0.03087   0.0115   0.0161   1.0000
   8.250   0.8564   0.04178   0.03438   0.0139   0.0160   1.0000
   8.500   0.8611   0.04510   0.03812   0.0164   0.0160   1.0000
   8.750   0.8618   0.04856   0.04198   0.0189   0.0161   1.0000
   9.000   0.8585   0.05211   0.04588   0.0215   0.0162   1.0000
   9.250   0.8507   0.05570   0.04978   0.0238   0.0164   1.0000
   9.500   0.8377   0.05923   0.05355   0.0262   0.0165   1.0000
   9.750   0.8215   0.06239   0.05687   0.0283   0.0167   1.0000
  10.000   0.8033   0.06627   0.06090   0.0285   0.0169   1.0000
  10.250   0.7852   0.07089   0.06566   0.0267   0.0170   1.0000
  10.500   0.7666   0.07669   0.07156   0.0231   0.0172   1.0000
  10.750   0.7482   0.08383   0.07878   0.0180   0.0174   1.0000
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